2results about "Generator circuit arrangements control" patented technology

An aircraft turbine engine including at least a propulsion shaft and an electric motor. A rotor is rigidly connected to the propulsion shaft. The electric motor includes at least three power channels, a control device designed to determine a control parameter for each power channel on the basis of a control command, and a correction device designed to correct a precession movement of the rotor relative to the stator. The correction device being designed to determine the control command of the control device from a setpoint command and a precession level. The control command being designed to generate a global magnetic force opposing the precession movement of the rotor so as to damp said movement.

There is described an electric power generating apparatus having: a free-piston linear expander having a moving shaft creating mechanical power; an electrical generator converting the mechanical power into electrical power; a variable frequency drive configured for applying an electromagnetic load force modifying the shaft's movement; and a controller communicatively coupled to the variable frequency drive, the controller configured to perform the steps of: receiving sensor data including a first shaft position value, a first shaft velocity value, and a first electromagnetic load force value; using a drive control module, determining, based on the sensor, a second electromagnetic load force value which when applied would cause a shaft velocity to gradually change to a second shaft velocity value, the second electromagnetic load force value and the second shaft velocity value causing an output power value to correspond to a desired output power value; and applying the second electromagnetic load force value.